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Planetary spacecraft - SEPS interface designThe interactions between a spacecraft which would rendezvous with the comet Tempel II, the stage, and the mission design are summarized along with solar electric propulsion system design issues. Attention is given to data communication, the spacecraft pointing control system, spacecraft power, plasma interactions, the release of a probe to study the comet Halley, and thruster usage. It was concluded that for a planetary mission design using a low-thrust stage, the control of the mission should reside in the payload spacecraft and that the power should be provided by the stage; the NASA standard 28 VDC bus is recommended.
Document ID
19800057347
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Pless, L. C.
(California Institute of Technology, Jet Propulsion Laboratory, Electric Propulsion and Advanced Concepts Group, Pasadena Calif., United States)
Date Acquired
August 10, 2013
Publication Date
June 1, 1980
Subject Category
Spacecraft Design, Testing And Performance
Report/Patent Number
AIAA PAPER 80-1227
Meeting Information
Meeting: Joint Propulsion Conference
Location: Hartford, CT
Start Date: June 30, 1980
End Date: July 2, 1980
Sponsors: AIAA, SAE, and ASME,
Accession Number
80A41517
Funding Number(s)
CONTRACT_GRANT: NAS7-100
Distribution Limits
Public
Copyright
Other

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